| 摘要 |
The invention relates to a thrust reverser (14) for a bypass turbojet engine nacelle (1), comprising at least one moving cowl (9) having an internal wall (26) intended to delimit, when the turboject engine is in a direct jet position, an external wall of an annular duct (6) through which a secondary or bypass flow flows, the reverser (14) comprising at least one flap (11) mounted in an articulated manner on the moving cowl (9) and actuated by at least one link rod (12) as the moving cowl (9) moves in the downstream direction so that in a reverse-thrust position each flap (11) comprises a zone (36) extending into the annular duct (6) so as to deflect at least some of the secondary or bypass flow out of said annular duct. At least one flap (11) has an extension (39) extending at least, in the reverse-thrust position, from said zone (36) as far as an external wall (25) of said moving cowl (9). |
